WORTMANN FX M2 AIRFOIL (fxm2-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: WORTMANN FX M2 AIRFOIL (fxm2-il) Reynolds number: 100,000 Max Cl/Cd: 45.93 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fxm2-il-100000.txt Download as CSV file: xf-fxm2-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX M2 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2698 0.09562 0.09102 -0.0153 1.0000 0.0488
-7.000 -0.2705 0.09360 0.08908 -0.0146 1.0000 0.0498
-6.750 -0.2739 0.09175 0.08732 -0.0136 1.0000 0.0509
-6.500 -0.2752 0.08975 0.08541 -0.0138 1.0000 0.0519
-6.250 -0.2747 0.08786 0.08361 -0.0159 1.0000 0.0530
-6.000 -0.2693 0.08628 0.08207 -0.0231 1.0000 0.0538
-5.750 -0.2617 0.08307 0.07891 -0.0262 1.0000 0.0543
-5.500 -0.2615 0.07946 0.07540 -0.0201 1.0000 0.0552
-5.250 -0.2572 0.07676 0.07278 -0.0182 1.0000 0.0565
-5.000 -0.2506 0.07420 0.07028 -0.0184 1.0000 0.0583
-4.750 -0.2403 0.07154 0.06764 -0.0206 1.0000 0.0613
-4.500 -0.2091 0.06820 0.06414 -0.0322 1.0000 0.0648
-4.250 -0.2124 0.06535 0.06146 -0.0269 1.0000 0.0664
-4.000 -0.2040 0.06298 0.05916 -0.0263 1.0000 0.0693
-3.750 -0.1602 0.06002 0.05585 -0.0380 1.0000 0.0757
-3.500 -0.1462 0.05607 0.05212 -0.0370 0.9959 0.0780
-3.250 -0.0805 0.05147 0.04724 -0.0494 0.9865 0.0881
-3.000 -0.0239 0.04752 0.04307 -0.0582 0.9767 0.1004
-2.750 0.0278 0.04349 0.03898 -0.0652 0.9669 0.1154
-2.500 0.0722 0.04005 0.03558 -0.0700 0.9530 0.1359
-1.750 0.2077 0.03120 0.02675 -0.0827 0.9039 0.2923
-1.250 0.2613 0.02654 0.02259 -0.0778 0.8529 0.4685
-1.000 0.2932 0.02455 0.02062 -0.0759 0.8167 0.5434
-0.750 0.4450 0.02086 0.01378 -0.1004 0.7625 0.1390
-0.500 0.4825 0.01994 0.01218 -0.1002 0.7081 0.1239
-0.250 0.5139 0.01955 0.01110 -0.0990 0.6583 0.1121
0.000 0.5411 0.01884 0.01004 -0.0980 0.6134 0.1080
0.250 0.5675 0.01852 0.00936 -0.0968 0.5733 0.1060
0.500 0.5933 0.01839 0.00889 -0.0956 0.5390 0.1090
0.750 0.6187 0.01824 0.00853 -0.0945 0.5057 0.1097
1.000 0.6436 0.01815 0.00823 -0.0933 0.4785 0.1109
1.250 0.6690 0.01821 0.00807 -0.0924 0.4543 0.1140
1.500 0.6950 0.01819 0.00794 -0.0917 0.4322 0.1233
1.750 0.7222 0.01835 0.00785 -0.0912 0.4154 0.1330
2.000 0.7500 0.01855 0.00792 -0.0908 0.3999 0.1621
2.250 0.7667 0.01711 0.00816 -0.0879 0.3872 1.0000
2.500 0.7937 0.01757 0.00831 -0.0873 0.3743 1.0000
2.750 0.8206 0.01805 0.00853 -0.0869 0.3633 1.0000
3.000 0.8475 0.01859 0.00880 -0.0865 0.3538 1.0000
3.250 0.8743 0.01917 0.00917 -0.0861 0.3441 1.0000
3.500 0.9007 0.01976 0.00969 -0.0858 0.3344 1.0000
3.750 0.9274 0.02037 0.01016 -0.0855 0.3265 1.0000
4.000 0.9537 0.02089 0.01063 -0.0851 0.3185 1.0000
4.250 0.9799 0.02143 0.01113 -0.0847 0.3111 1.0000
4.500 1.0064 0.02191 0.01148 -0.0843 0.3046 1.0000
4.750 1.0320 0.02248 0.01205 -0.0839 0.2974 1.0000
5.000 1.0589 0.02307 0.01244 -0.0837 0.2917 1.0000
5.250 1.0839 0.02380 0.01327 -0.0832 0.2852 1.0000
5.500 1.1106 0.02455 0.01392 -0.0830 0.2800 1.0000
5.750 1.1348 0.02536 0.01488 -0.0825 0.2740 1.0000
6.000 1.1606 0.02607 0.01552 -0.0821 0.2681 1.0000
6.250 1.1838 0.02680 0.01643 -0.0814 0.2613 1.0000
6.500 1.2098 0.02740 0.01693 -0.0811 0.2559 1.0000
6.750 1.2322 0.02814 0.01789 -0.0803 0.2491 1.0000
7.000 1.2579 0.02870 0.01832 -0.0800 0.2437 1.0000
7.250 1.2804 0.02947 0.01922 -0.0792 0.2369 1.0000
7.500 1.3046 0.03030 0.02004 -0.0788 0.2311 1.0000
7.750 1.3272 0.03120 0.02100 -0.0781 0.2245 1.0000
8.000 1.3485 0.03236 0.02229 -0.0774 0.2182 1.0000
8.250 1.3707 0.03331 0.02330 -0.0767 0.2121 1.0000
8.500 1.3898 0.03460 0.02480 -0.0757 0.2065 1.0000
8.750 1.4101 0.03567 0.02605 -0.0748 0.2011 1.0000
9.000 1.4330 0.03668 0.02705 -0.0743 0.1971 1.0000
9.250 1.4469 0.03835 0.02911 -0.0728 0.1919 1.0000
9.500 1.4680 0.03931 0.03012 -0.0721 0.1882 1.0000
9.750 1.4937 0.04019 0.03091 -0.0719 0.1854 1.0000
10.000 1.4986 0.04297 0.03426 -0.0698 0.1818 1.0000
10.250 1.5083 0.04531 0.03692 -0.0682 0.1788 1.0000
10.500 1.5213 0.04726 0.03907 -0.0670 0.1762 1.0000
10.750 1.5367 0.04895 0.04088 -0.0660 0.1741 1.0000
11.000 1.5555 0.05056 0.04255 -0.0654 0.1722 1.0000
11.250 1.5621 0.05356 0.04577 -0.0640 0.1706 1.0000
11.500 1.5390 0.05848 0.05123 -0.0607 0.1693 1.0000
11.750 1.4975 0.06443 0.05763 -0.0568 0.1686 1.0000
12.000 1.4182 0.07357 0.06711 -0.0540 0.1688 1.0000
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Polar data table (+)
Polar graphs
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